JPH01242743A - Heat-resistant titanium alloy - Google Patents
Heat-resistant titanium alloyInfo
- Publication number
- JPH01242743A JPH01242743A JP6861588A JP6861588A JPH01242743A JP H01242743 A JPH01242743 A JP H01242743A JP 6861588 A JP6861588 A JP 6861588A JP 6861588 A JP6861588 A JP 6861588A JP H01242743 A JPH01242743 A JP H01242743A
- Authority
- JP
- Japan
- Prior art keywords
- strength
- content
- alloy
- creep
- titanium alloy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 32
- 239000012535 impurity Substances 0.000 claims abstract description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 abstract description 10
- 239000000956 alloy Substances 0.000 abstract description 10
- 239000000463 material Substances 0.000 abstract description 5
- 229910052782 aluminium Inorganic materials 0.000 abstract description 4
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 238000009864 tensile test Methods 0.000 description 9
- 230000000052 comparative effect Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 239000000203 mixture Substances 0.000 description 3
- 239000002244 precipitate Substances 0.000 description 3
- 230000000087 stabilizing effect Effects 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 229910021330 Ti3Al Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005098 hot rolling Methods 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 1
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は、耐熱チタン合金、特に、高温強度およびク
リープ強度に優れた耐熱チタン合金に関するものである
。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a heat-resistant titanium alloy, particularly a heat-resistant titanium alloy that has excellent high-temperature strength and creep strength.
チタン合金は軽くて強靭な機械的性質を有し。 Titanium alloys are lightweight and have strong mechanical properties.
特に、４５０℃程度までの温度域において高い比強度（
強度／密度）を示すことから、航空機用ジェットエンジ
ン材料として近年盛んに用いられている。チタン合金の
中で、最も一般に用いられているのはＴｉ −６Ａｔ−
４Ｖ合金であるが、この合金の使用可能温度範囲はせい
ぜい３００℃程度までである。この合金の耐熱性を高め
た合金として、Ｔｉ−６２４２８合金がＵ８パテント３
，８３３，３６３に開示されている。In particular, high specific strength (
In recent years, it has been widely used as an aircraft jet engine material because of its high strength/density. Among titanium alloys, the most commonly used is Ti-6At-
Although it is a 4V alloy, the usable temperature range of this alloy is at most about 300°C. As an alloy with improved heat resistance of this alloy, Ti-62428 alloy is U8 Patent 3
, 833, 363.
ジェットエンジン用チタン合金に要求される特性には、
高温強度、耐クリープ特性、耐酸化性などがあり、また
製造上、優れた鍛造性および溶接性も求められる。Ｔｉ
−６２４２８合金は、Ｓｉを添加することにより生じ
るコットレル効果により転位運動を抑え、高温強度やク
リープ強度を上昇させている。しかしながら、Ｓｉは高
温強度の小さいβ相安定化元素であるため、その効果は
５５０℃程度の温度域までであった。The properties required for titanium alloys for jet engines include:
It has high temperature strength, creep resistance, oxidation resistance, etc., and also requires excellent forgeability and weldability in manufacturing. Ti
-62428 alloy suppresses dislocation motion due to the Cottrell effect caused by adding Si, and increases high temperature strength and creep strength. However, since Si is a β-phase stabilizing element with low high-temperature strength, its effect was limited up to a temperature range of about 550°C.
そのため、これらのチタン合金も、航空機の高速度化を
目的とした高効率ジェットエンジンの開発の点からは十
分とは言えず、更に高温特性に優れた耐熱チタン合金の
開発が望まれている。Therefore, these titanium alloys are not sufficient from the point of view of developing high-efficiency jet engines aimed at increasing the speed of aircraft, and there is a desire to develop heat-resistant titanium alloys with even better high-temperature properties.
そこで、この発明の目的は、上記従来の合金よりも高温
強度およびクリープ強度に優れた耐熱チタン合金を提供
することにある。Therefore, an object of the present invention is to provide a heat-resistant titanium alloy that has superior high-temperature strength and creep strength to the conventional alloys.
この発明は、Ａ１：５．ｓから６．５％、Ｓｎ：１．５
から３．０ ％、 Ｚｒ ： ０．７から５．０ ’％
、 Ｍｏ ： ０．７から３．０％、ｓｌ：ｏ、ｏ４か
ら０．１５％、Ｃ：０．０４から０．３０％、Ｏ：０．
１６％以下（以上重量％）、残り：Ｔ１および不可避不
純物からなり、且つ、Ａｅ−二十一と−：６．５から８
．０重量％を満足することに特徴を有するものである。This invention has A1:5. 6.5% from s, Sn: 1.5
to 3.0%, Zr: 0.7 to 5.0'%
, Mo: 0.7 to 3.0%, sl: o, 0.15% from o4, C: 0.04 to 0.30%, O: 0.
16% or less (weight% or more), remainder: consisting of T1 and inevitable impurities, and Ae-21 and -: 6.5 to 8
．． It is characterized by satisfying 0% by weight.
次に、この発明において成分組成を上記範囲に限定した
理由について説明する。Next, the reason why the component composition is limited to the above range in this invention will be explained.
Ａｇ ： Ａｌは、α＋βの二相組織を得るためのα相
安定化元素として添加され、且つ強度上昇に寄与する。Ag: Al is added as an α-phase stabilizing element to obtain an α+β two-phase structure, and also contributes to increasing strength.
しかし、含有量が５．５％未満では、目的とする引張強
さ（特に高温強度）およびクリープ強度が得られず、一
方、含有量が６．５％を超えると、Ｔ１との間に脆化相
である、α２相（Ｔｉ３Ａｔ ）が析出して、機械的性
質（特に延性）を劣化させる。従って、この発明におい
ては、Ｍの添加量を５．５から６．５重量％の範囲に限
定した。However, if the content is less than 5.5%, the desired tensile strength (especially high-temperature strength) and creep strength cannot be obtained, while if the content exceeds 6.5%, the relationship between T1 and T1 is brittle. α2 phase (Ti3At), which is a chemical phase, precipitates and deteriorates mechanical properties (especially ductility). Therefore, in this invention, the amount of M added is limited to a range of 5.5 to 6.5% by weight.
Ｓｎ： Ｓｎは、中性元素としてα相およびβ相の両方
に固溶し、強度上昇に寄与する。しかし、含有量が１．
５％未満では、目的とする強度が得られず、一方、含有
量が３．０％を超えると、密度が大きくなり、高比強度
であるというチタン合金の長所が損なわれ、しかも、
Ｔｉとの間に脆化相であるα２ 相（ｑｔｓｕ）が析出
して、機械的性質（特に延性）を劣化させる。従つて、
この発明においては、Ｓｏの添加量を１．５から３．０
重量％の範囲内に限定した。Sn: Sn is a neutral element that dissolves in solid solution in both the α phase and the β phase, and contributes to an increase in strength. However, the content is 1.
If the content is less than 5%, the desired strength cannot be obtained, while if the content exceeds 3.0%, the density increases and the advantage of titanium alloys, which is high specific strength, is lost.
An α2 phase (qtsu), which is a brittle phase, precipitates between Ti and deteriorates mechanical properties (especially ductility). Therefore,
In this invention, the amount of So added is 1.5 to 3.0.
It was limited within the range of % by weight.
Ｚｒ： Ｚｒは、中性元素としてα相およびβ相の両方
に固溶し１強度上昇に寄与する。しかし、含有量が０．
７％未満では、目的とする強度が得られず、一方、含有
量が５．０％を超えると、クリープ強度の小さいβ相の
体積率が大きくな９、クリープ強度が低下する。従って
、この発明においては、Ｚｒの添加量を０．７ から５
．０重量％の範囲内に限定した。Zr: Zr is a neutral element that is dissolved in solid solution in both the α phase and the β phase and contributes to an increase in strength. However, the content is 0.
If the content is less than 7%, the desired strength cannot be obtained, while if the content exceeds 5.0%, the volume fraction of the β phase, which has low creep strength, becomes large9, resulting in a decrease in creep strength. Therefore, in this invention, the amount of Zr added is from 0.7 to 5.
．． It was limited to 0% by weight.
Ｍｏ：Ｍｏは、β相安定化元素として添加され、強度上
昇、特に室温強度の上昇に寄与する。しかし、含有量が
０．７％未満では、目的とする強度が得られず、一方、
含有量が３．０チを超えると、Ｚｒの添加の場合と同様
、高温強度やクリープ強度を低下させる。従って、この
発明においては ’ｋＡｏの添加量を０．ＴＩから３．
０重量−の範囲内に限定した。Mo: Mo is added as a β-phase stabilizing element and contributes to increasing strength, particularly room temperature strength. However, if the content is less than 0.7%, the desired strength cannot be obtained;
If the content exceeds 3.0 g, the high temperature strength and creep strength will be reduced as in the case of adding Zr. Therefore, in this invention, the amount of 'kAo added is 0. 3 from TI.
It was limited to a range of 0 weight.
Ｓｉ： Ｓｉは、高温時の転位運動をコットレル効果に
より抑え、高温強度やクリープ強度の上昇に寄与する。Si: Si suppresses dislocation motion at high temperatures through the Cottrell effect, contributing to increases in high temperature strength and creep strength.
しかし、含有量が０．０４％未満では、目的とする強度
が得られず、一方、含有量が０．１５％を超えると、Ｔ
１と８１との化合物（Ｔｉ５Ｓ１３等）を形成し、延性
等の機械的性質を劣化させ、しかも、５５０℃以上の温
度域において高温強度やクリープ強度の低下をもたらす
。However, if the content is less than 0.04%, the desired strength cannot be obtained, while if the content exceeds 0.15%, the T
1 and 81 (such as Ti5S13), which deteriorates mechanical properties such as ductility, and also causes a decrease in high temperature strength and creep strength in a temperature range of 550° C. or higher.
従って、この発明においては、Ｓｉの添加量を０．０４
から０．１５重量％の範囲内に限定した。Therefore, in this invention, the amount of Si added is 0.04
The content was limited to 0.15% by weight.
Ｃ：Ｃは、主にα相に固溶し、室温の強度上昇のみなら
ず、高温強度とクリープ強度の上昇に寄与する。しかし
ながら、含有量が０．０４％未満では、目的とする強度
が得られず、一方、含有量がｏ、３ｏ％を超えるとチタ
ンの炭化物が析出して、延性を損なう。従って、この発
明においては、Ｃの添加量を０．０４から０．３０重量
％の範囲内に限定した。C: C is mainly dissolved in the α phase and contributes not only to an increase in strength at room temperature but also to an increase in high temperature strength and creep strength. However, if the content is less than 0.04%, the desired strength cannot be obtained, while if the content exceeds 30%, titanium carbide will precipitate, impairing ductility. Therefore, in this invention, the amount of C added is limited to within the range of 0.04 to 0.30% by weight.
０：０は、主にα相に固溶し、室温の強度上昇のみなら
ず、高温強度とクリープ強度の上昇に寄与する。しかし
ながら、含有量が０．１６％を超えると延性が低下する
。従って、この発明においては、０の添加量を０．１６
重量％以下に限定した。0:0 is mainly dissolved in the α phase and contributes not only to an increase in strength at room temperature but also to an increase in high temperature strength and creep strength. However, when the content exceeds 0.16%, ductility decreases. Therefore, in this invention, the amount of 0 added is 0.16
It was limited to % by weight or less.
Ｍ −１−−４−−、６，５から８．０重量％に限定し
たのは、次の理由による。即ち、これはチタン合金のア
ルミ当量と呼ばれ、この値が８％を超えると。The reason why M -1--4-- was limited to 6.5 to 8.0% by weight is as follows. That is, this is called the aluminum equivalent of titanium alloy, and if this value exceeds 8%.
Ｔｉ３Ａｌ等の金属間化合物が生成し、延性を損なうの
で好ましくない。また、この値が６．５％未満では、室
温強度、高温強度およびクリープ強度が小さくなる。従
って、この発明においては、上記値を６．５から８．０
重量％の範囲内に限定した。This is not preferable because intermetallic compounds such as Ti3Al are generated and impair ductility. Furthermore, if this value is less than 6.5%, the room temperature strength, high temperature strength, and creep strength will decrease. Therefore, in this invention, the above value is set to 6.5 to 8.0.
It was limited within the range of % by weight.
アルゴンガス雰囲気アーク溶解炉にてインゴットを溶製
した。これを、熱間鍛造および熱間圧延を行い、厚さマ
ーの板材に加工した。β晶の粗大化を防ぐため、および
、等軸α晶組織を得るために、熱間圧延時の加熱を、β
変態点を３０℃下回る温度で実施した。これらの材料を
、β変態点を１５〜３０℃下回る温度にて１時間焼鈍し
、この後、空冷し、さらに、６００℃にて８時間の時効
処理を行い、供試材とした。本発明チタン合金の成分組
成および室温引張試験の結果を第１表に示し、高温引張
試験およびクリープ試験の結果を第３表に示す。また、
従来チタン合金、比較チタン合金の成分組成および室温
引張試験の結果を第２表に示し、高温引張試験およびク
リープ試験の結果を第４表に示す。ただし、比較チタン
合金１６゜１７および２２は、室温引張シ試験時の伸び
が１０チ未満と小さく、実用に耐えないため、高温引張
り試験及びクリープ試験を実施しなかった。第３表およ
び第４表に示す高温引張試験は、６００℃においておこ
なったものである。また、同表中の最小クリープ速度（
％／ｈ、ｒ ）は、温度５１０℃、応力ｚ４．６Ｋｇｔ
／−において行ったクリープ試験の時間−伸び曲線から
求めたものである。高温引張試験およびクリープ試験は
、大気中で実施した。An ingot was melted in an argon gas atmosphere arc melting furnace. This was hot-forged and hot-rolled to form a plate material with a thickness of 1. In order to prevent the coarsening of β crystals and to obtain an equiaxed α crystal structure, heating during hot rolling is
It was carried out at a temperature 30°C below the transformation point. These materials were annealed for 1 hour at a temperature 15 to 30°C below the β transformation point, then air cooled, and then aged at 600°C for 8 hours to obtain test materials. The composition of the titanium alloy of the present invention and the results of the room temperature tensile test are shown in Table 1, and the results of the high temperature tensile test and creep test are shown in Table 3. Also,
The compositions and room temperature tensile test results of the conventional titanium alloy and comparative titanium alloy are shown in Table 2, and the results of the high temperature tensile test and creep test are shown in Table 4. However, the comparative titanium alloys 16°17 and 22 had a small elongation of less than 10 inches during the room temperature tensile test, and were not suitable for practical use, so high temperature tensile tests and creep tests were not conducted. The high temperature tensile tests shown in Tables 3 and 4 were conducted at 600°C. In addition, the minimum creep rate (
%/h, r ) is at a temperature of 510°C and a stress of 4.6 kgt.
It was determined from the time-elongation curve of the creep test conducted at /-. High temperature tensile tests and creep tests were conducted in air.
第 ３ 表
第 ４ 表
第３表から明らかなように１本発明チタン合金は、６０
０℃における高温引張強度が６７にｇｔ／ｄ以上と大き
く、しかも、５１０℃、応力２４．６Ｋｇ ｆ／−にお
ける最小クリープ速度が、０．６４Ｘ１０−３％／ｈｒ
以下と小さく、比較チタン合金および従来チタン合
金Ｔｉ −６Ａｔ −４Ｖ 、 Ｔｉ −６ＡＬ−２Ｓ
ｎ −４Ｚｒ−２Ｍｏと比較して非常に優れている。ま
た、本発明チタン合金は、室温においても１ｏ５ＫＢ／
−以上の大きな引張強さと１ｚ、ｓ％以上の大きな伸び
とを合わせ持っておシ、室温から高温までの広い温度範
囲において、非常に優れた機械的性質を有していること
がわかる。As is clear from Table 3, the titanium alloy of the present invention has a
The high temperature tensile strength at 0℃ is as high as 67 gt/d or more, and the minimum creep rate at 510℃ and stress 24.6Kg f/- is 0.64X10-3%/hr.
Comparative titanium alloys and conventional titanium alloys Ti-6At-4V, Ti-6AL-2S
It is very superior compared to n-4Zr-2Mo. Furthermore, the titanium alloy of the present invention has a capacity of 1o5KB/ even at room temperature.
It can be seen that it has a large tensile strength of - or more and a large elongation of 1z, s% or more, and has very excellent mechanical properties in a wide temperature range from room temperature to high temperature.
第１図に、横軸にＣ含有量（重量％）を、縦軸に温度５
１０℃、応力２４．６〜で／−のクリープ試験における
最小クリープ速度を示す。ここにおいて、曲線における
実線の部分１は、本発明チタン合金の実験値をプロット
した部分を示し、点線の部分２は、比較チタン合金の実
験値をプロットした部分を示し、Δ印３は従来チタン合
金の実験値をプロットした点を示す。In Figure 1, the horizontal axis shows C content (wt%), and the vertical axis shows temperature 5.
The minimum creep rate in the creep test at 10° C. and stress 24.6 to /− is shown. Here, the solid line part 1 of the curve shows the part where the experimental values of the titanium alloy of the present invention are plotted, the dotted line part 2 shows the part where the experimental values of the comparative titanium alloy are plotted, and the Δ mark 3 shows the part where the experimental values of the titanium alloy of the present invention are plotted. Shows the points where experimental values for the alloy are plotted.
第１図から明らかなように、Ｃ含有量が０．０４〜０．
３０重量％の範囲で０．６４ Ｘ １０””以下の最小
クリープ速度の値を示しており、その範囲に満たないＣ
含有量（重量％）では、最小クリープ速度が大きい。一
方、Ｃ含有量（重量％）をその範囲を超えて添加すると
、最小クリープ速度は良くならず、第２表かられかるよ
うに室温における延性が５．６％と非常に劣化する。As is clear from FIG. 1, the C content is between 0.04 and 0.04.
It shows a minimum creep rate value of 0.64 x 10" or less in the range of 30% by weight, and C
The minimum creep rate is high for the content (wt%). On the other hand, when the C content (wt%) is added beyond this range, the minimum creep rate does not improve, and as shown in Table 2, the ductility at room temperature deteriorates significantly to 5.6%.
第２図において、横軸にＣ含有量（重量％）を、縦軸に
温度６００℃における引張試験の結果を示す。ここにお
いて、曲線における実線の部分１は、本発明チタン合金
の実験値をプロットした部分を示し、点線の部分２は比
較チタン合金および従来チタン合金の実験値をプロット
した部分を示す。In FIG. 2, the horizontal axis shows the C content (% by weight), and the vertical axis shows the results of a tensile test at a temperature of 600°C. Here, the solid line section 1 of the curve indicates the section where the experimental values of the titanium alloy of the present invention are plotted, and the dotted line section 2 indicates the section where the experimental values of the comparative titanium alloy and the conventional titanium alloy are plotted.
第２図から明らかなように、Ｃ含有量が０．０４〜０．
３０重量％の範囲で６７にｙ ｆ／ｌ！ｊ 以上の引
張強さを示しておシ、その範囲に満たないＣ含有量（重
量％）では、引張強さが小さい。As is clear from FIG. 2, the C content ranges from 0.04 to 0.
y f/l to 67 in the range of 30% by weight! If the C content (wt%) is less than that range, the tensile strength is small.
これらのことから、Ｃ含有量が０．０４〜０．３０重量
％の範囲において、優れた機械的性質（室温強度、高温
強度およびクリープ強度）が得られることが明らかとな
った。These results revealed that excellent mechanical properties (room temperature strength, high temperature strength, and creep strength) can be obtained when the C content is in the range of 0.04 to 0.30% by weight.
以上説明したように、この発明によれば、Ｃ含有量を０
．０４〜０．３０重量％の範囲にすることによって、室
温から高温までの広い温度範囲において、大きな引張強
度およびクリープ強度を得ることができ、その結果、航
空宇宙用材料を始めとして、その優れた比強度、高温特
性から、各種産業分野において広く用いることができる
といった有用な効果がもたらされる。As explained above, according to the present invention, the C content can be reduced to 0.
．． By setting the content in the range of 0.04 to 0.30% by weight, large tensile strength and creep strength can be obtained in a wide temperature range from room temperature to high temperature. Due to its specific strength and high-temperature properties, it has useful effects that allow it to be widely used in various industrial fields.
第１図は、本発明チタン合金、比較チタン合金、そして
従来チタン合金と最小クリープ速度との関係を示すグラ
フ、第２図は、本発明チタン合液、比較チタン合金、そ
して従来チタン合金と高温引張特性（０，２チ耐力およ
び引張強さ］との関係を示すグラフである。
第１図
Ｃ含有量 （重量％）Figure 1 is a graph showing the relationship between the minimum creep rate of the titanium alloy of the present invention, a comparative titanium alloy, and a conventional titanium alloy. It is a graph showing the relationship with tensile properties (0, 2 inch proof stress and tensile strength). Figure 1 C content (wt%)
Claims (1)
満足することを特徴とする耐熱チタン合金。[Claims] 1 Al: 5.5 to 6.5%, Sn: 1.5 to 3.0%, Zr: 0.7 to 5.0%, Mo: 0.7 to 3.0% , Si: 0.04 to 0.15%, C: 0.04 to 0.30%, O: 0.16% or less (weight%), remainder: consisting of Ti and inevitable impurities, and Al+Sn/3+Zr /6: A heat-resistant titanium alloy that satisfies 6.5 to 8.0% by weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63068615A JPH0621305B2 (en) | 1988-03-23 | 1988-03-23 | Heat resistant titanium alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63068615A JPH0621305B2 (en) | 1988-03-23 | 1988-03-23 | Heat resistant titanium alloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01242743A true JPH01242743A (en) | 1989-09-27 |
| JPH0621305B2 JPH0621305B2 (en) | 1994-03-23 |
Family
ID=13378841
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63068615A Expired - Lifetime JPH0621305B2 (en) | 1988-03-23 | 1988-03-23 | Heat resistant titanium alloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0621305B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000005425A1 (en) * | 1998-07-21 | 2000-02-03 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Titanium-based composite material, method for producing the same and engine valve |
| JP2009531546A (en) * | 2006-03-30 | 2009-09-03 | スネクマ | Heat treatment method and manufacturing method for thermomechanical components made of titanium alloy, and thermomechanical components obtained from these methods |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2797996A (en) * | 1953-12-07 | 1957-07-02 | Rem Cru Titanium Inc | Titanium base alloys |
| JPS4915611A (en) * | 1972-04-04 | 1974-02-12 | ||
| US3833363A (en) * | 1972-04-05 | 1974-09-03 | Rmi Co | Titanium-base alloy and method of improving creep properties |
| JPS5989744A (en) * | 1982-10-15 | 1984-05-24 | アイエムアイ・チタニウム・リミテツド | Weldable titanium alloy |
| US4639281A (en) * | 1982-02-19 | 1987-01-27 | Mcdonnell Douglas Corporation | Advanced titanium composite |
-
1988
- 1988-03-23 JP JP63068615A patent/JPH0621305B2/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2797996A (en) * | 1953-12-07 | 1957-07-02 | Rem Cru Titanium Inc | Titanium base alloys |
| JPS4915611A (en) * | 1972-04-04 | 1974-02-12 | ||
| US3833363A (en) * | 1972-04-05 | 1974-09-03 | Rmi Co | Titanium-base alloy and method of improving creep properties |
| US4639281A (en) * | 1982-02-19 | 1987-01-27 | Mcdonnell Douglas Corporation | Advanced titanium composite |
| JPS5989744A (en) * | 1982-10-15 | 1984-05-24 | アイエムアイ・チタニウム・リミテツド | Weldable titanium alloy |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000005425A1 (en) * | 1998-07-21 | 2000-02-03 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Titanium-based composite material, method for producing the same and engine valve |
| US6551371B1 (en) | 1998-07-21 | 2003-04-22 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Titanium-based composite material, method for producing the same and engine valve |
| KR100398547B1 (en) * | 1998-07-21 | 2003-09-19 | 도요타지도샤가부시키가이샤 | Titanium-based composite material, method for producing the same and engine valve |
| JP2009531546A (en) * | 2006-03-30 | 2009-09-03 | スネクマ | Heat treatment method and manufacturing method for thermomechanical components made of titanium alloy, and thermomechanical components obtained from these methods |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0621305B2 (en) | 1994-03-23 |
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